U.S. patent application number 15/682785 was filed with the patent office on 2018-03-08 for satellite system using optical gateways and ground based beamforming.
This patent application is currently assigned to SPACE SYSTEMS/LORAL, LLC. The applicant listed for this patent is Space Systems/Loral, LLC. Invention is credited to Vijaya Gallagher, Ghislain Turgeon, Leah Wang.
Application Number | 20180069629 15/682785 |
Document ID | / |
Family ID | 59790978 |
Filed Date | 2018-03-08 |
United States Patent
Application |
20180069629 |
Kind Code |
A1 |
Turgeon; Ghislain ; et
al. |
March 8, 2018 |
SATELLITE SYSTEM USING OPTICAL GATEWAYS AND GROUND BASED
BEAMFORMING
Abstract
Described herein are ground based subsystems, and related
methods, for use in transmitting an optical feeder uplink beam to a
satellite that includes a multiple element antenna feed array and
that is configured to accept the optical feeder uplink beam and in
dependence thereon use the multiple element antenna feed array to
produce and transmit a plurality of radio frequency (RF) service
downlink beams to service terminals. Certain embodiments are
related to a ground based beamformer (GBBF) for inclusion in a
ground based subsystem, and methods for use therewith.
Beneficially, embodiments described herein allow for flexible
antenna beam forming for large signal bandwidth without the
limitation associated with the available gateway uplink and
downlink spectrum at RF frequencies. Also described herein are
space based subsystems for use with such ground based
subsystems.
Inventors: |
Turgeon; Ghislain; (San
Jose, CA) ; Gallagher; Vijaya; (Palo Alto, CA)
; Wang; Leah; (Fremont, CA) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Space Systems/Loral, LLC |
Palo Alto |
CA |
US |
|
|
Assignee: |
SPACE SYSTEMS/LORAL, LLC
Palo Alto
CA
|
Family ID: |
59790978 |
Appl. No.: |
15/682785 |
Filed: |
August 22, 2017 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
62384604 |
Sep 7, 2016 |
|
|
|
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
H04B 10/272 20130101;
H04B 10/25 20130101; H04B 10/70 20130101; H04B 10/1121 20130101;
H01Q 1/288 20130101; H04B 10/118 20130101; H04B 10/90 20130101;
H04B 10/80 20130101; H04B 10/112 20130101 |
International
Class: |
H04B 10/118 20060101
H04B010/118; H01Q 1/28 20060101 H01Q001/28; H04B 10/112 20060101
H04B010/112; H04B 10/25 20060101 H04B010/25; H04B 10/272 20060101
H04B010/272; H04B 10/00 20060101 H04B010/00; H04B 10/80 20060101
H04B010/80 |
Claims
1. A ground based subsystem for use in transmitting an optical
feeder uplink beam to a satellite that includes a multiple element
antenna feed array and that is configured to input the optical
feeder uplink beam and in dependence thereon use the multiple
element antenna feed array to produce and transmit a plurality of
RF service downlink beams to service terminals, the ground based
subsystem comprising: a ground based beamformer (GBBF) configured
to accept a plurality of spot beam signals, produce or otherwise
obtain phase and amplitude beamforming coefficients, and output a
plurality of feed element signals in dependence on the plurality of
spot beam signals and the phase and amplitude beamforming
coefficients; a plurality of lasers, each of the lasers operable to
emit an optical signal having a different peak wavelength within a
specified optical wavelength range; a plurality of electro-optical
modulators (EOMs), each EOM of the plurality of EOMs configured to
accept an optical carrier signal from a respective one of the
plurality of lasers, accept a different one of the plurality of
feed element signals from the GBBF, which may be frequency
up-converted and filtered prior to being accepted by the EOM, and
output a respective optical feed element signal in dependence on
the optical carrier signal and the feed element signal accepted by
the EOM; a wavelength-division multiplexing (WDM) multiplexer
configured to accept the optical feed element signals output by the
plurality of EOMs, and combine the plurality of optical feed
element signals into a wavelength division multiplexed optical
signal; an optical amplifier configured to amplify the wavelength
division multiplexed optical signal to thereby produce an optically
amplified wavelength division multiplexed optical signal; and
transmitter optics configured to accept the optically amplified
wavelength division multiplexed optical signal and transmit an
optical feeder uplink beam to the satellite in dependence
thereon.
2. The subsystem of claim 1, further comprising: a user data to
spot beam controller configured to accept a set of user data
signals and combine subsets of the user data signals into the spot
beam signals that are provided to the GBBF.
3. The subsystem of claim 1, wherein the GBBF is further configured
to: produce multiple copies of each of the spot beam signals
accepted by the GBBF; use the phase and amplitude coefficients to
weight different copies of the spot beam signals in different
manners; and sum subsets of the weighted copies of the spot beam
signals to thereby produce the feed element signals, which may be
frequency up-converted and filtered prior to being accepted by the
EOMs.
4. The subsystem of claim 1, further comprising: a plurality of
frequency up-converters each of which is configured to frequency-up
convert one of the feed element signals output by the GBBF before
the feed element signal is provided to one of the EOMs; and a
plurality of filters each of which is configured to filter one of
the feed element signals after the feed element signal has been
frequency up-converted, but prior to the feed element signal being
provided to one of the EOMs.
5. The subsystem of claim 4, wherein the frequency up-converters
are configured to cause the the optical feed element signals output
by the plurality of EOMs to each have an RF frequency within a same
specified RF frequency range within which the satellite is
configured to transmit the plurality of RF service downlink
beams.
6. The subsystem of claim 1, wherein: the optical feed element
signals output by the plurality of EOMs each have an RF frequency
within a same specified RF frequency range within which the
satellite is configured to transmit the plurality of RF service
downlink beams; and because RF frequencies of the optical feed
element signals output by the plurality of EOMs are within the same
specified RF frequency range within which the satellite is
configured to transmit the plurality of RF service downlink beams,
there is an elimination of any need for the satellite to perform
any frequency conversions when producing the plurality of RF
service downlink beams in dependence on the optical feeder uplink
beam.
7. The subsystem of claim 1, wherein a specified RF frequency range
within which the satellite is configured to produce and transmit
the plurality of RF service downlink beams comprises a downlink
portion of the Ka band.
8. The subsystem of claim 7, wherein: the downlink portion of the
Ka band is from 17.7 GHz to 20.2 GHz, and thus, has a bandwidth of
2.5 GHz; or the downlink portion of the Ka band is from 17.3 GHz to
20.2 GHz, and thus, has a bandwidth of 2.9 GHz.
9. The subsystem of claim 1, wherein an optical wavelength range of
the optical feeder uplink beam is a contiguous or non-contiguous
optical wavelength range within an infrared (IR) spectrum.
10. A method for enabling a ground based subsystem to produce and
transmit an optical feeder uplink beam to a satellite that includes
a multiple element antenna feed array and that is configured to
accept the optical feeder uplink beam and in dependence thereon use
the multiple element antenna feed array to produce and transmit a
plurality of RF service downlink beams to service terminals, the
method for use by the ground based subsystem comprising: performing
ground based beamforming by accepting a plurality of spot beam
signals, producing or otherwise obtaining phase and amplitude
beamforming coefficients, and producing a plurality of feed element
signals in dependence on the plurality of spot beam signals and the
phase and amplitude beamforming coefficients; emitting a plurality
of optical carrier signals each having a different peak wavelength
that is within a specified optical wavelength range;
electro-optically modulating each of the optical carrier signals
with one of feed element signals produced by the ground based
beamforming to thereby produce a plurality of optical feed element
signals, wherein the feed element signals may be frequency
up-converted and filtered prior to the electro-optically
modulating; multiplexing the plurality of optical feed element
signals to thereby produce a wavelength division multiplexed
optical signal that includes data for the plurality of RF service
downlink beams; producing an optical feeder uplink beam, in
dependence on the wavelength division multiplexed optical signal;
and transmitting the optical feeder uplink beam through free-space
to the satellite.
11. The method of claim 10, further comprising: accepting a set of
user data signals; and combining subsets of the user data signals
into the spot beam signals that are used for the ground based
beamforming.
12. The method of claim 10, wherein the ground based beamforming
further comprises: producing multiple copies of each of the spot
beam signals; using the phase and amplitude coefficients to weight
different copies of the spot beam signals in different manners; and
summing subsets of the weighted copies of the spot beam signals to
thereby produced the feed element signals, which may be frequency
up-converted and filtered prior to the electro-optically
modulating.
13. The method of claim 10, further comprising: frequency-up
converting and filtering the feed element signals produced by the
ground based beamforming prior to the electro-optically
modulating.
14. The method of claim 13, wherein the frequency up-converting
causes the the optical feed element signals resulting from the
electro-optically modulating to each have an RF frequency within a
same specified RF frequency range within which the satellite is
configured to transmit the plurality of RF service downlink
beams.
15. The method of claim 10, wherein: the optical feed element
signals resulting from the electro-optically modulating each have
an RF frequency within a same specified RF frequency range within
which the satellite is configured to transmit the plurality of RF
service downlink beams; and because RF frequencies of the optical
feed element resulting from the electro-optically modulating are
within the same specified RF frequency range within which the
satellite is configured to transmit the plurality of RF service
downlink beams, there is an elimination of any need for the
satellite to perform any frequency conversions when producing the
plurality of RF service downlink beams in dependence on the optical
feeder uplink beam.
16. A ground based subsystem for use in transmitting an optical
feeder uplink beam to a satellite that includes a multiple element
antenna feed array and that is configured to accept the optical
feeder uplink beam and in dependence thereon use the multiple
element antenna feed array to produce and transmit a plurality of
RF service downlink beams to service terminals, the ground based
subsystem comprising: a ground based beamformer (GBBF) including a
GBBF controller, a signal replication and forward beamforming
weighting unit that is controlled by the GBBF controller, and a
plurality of summers; the GBBF controller configured to produce
phase and amplitude beamforming coefficients in dependence on
calibration information accepted from a calibration subsystem; the
signal replication and forward beamforming weighting unit
configured to replicate each of a plurality of spot beam signals,
weight each of the replicated spot beam signals in dependence on
phase and amplitude beamforming coefficients produced by the GBBF
controller, and output a set of phase and amplitude weighted
signals; the plurality of summers configured to sum respective
subsets of the phase and amplitude weighted signals to thereby
produce a plurality of feed element signals; a plurality of lasers,
each of the lasers operable to emit an optical signal having a
different peak wavelength within a specified optical wavelength
range; a plurality of electro-optical modulators (EOMs), each EOM
of the plurality of EOMs configured to accept an optical carrier
signal from a respective one of the plurality of lasers, accept a
different one of the plurality of feed element signals from the
GBBF, which may be frequency up-converted and filtered prior to
being accepted by the EOM, and output a respective optical feed
element signal in dependence on the optical carrier signal and the
feed element signal accepted by the EOM; a wavelength-division
multiplexing (WDM) multiplexer configured to accept the optical
feed element signals output by the plurality of EOMs, and combine
the plurality of optical feed element signals into a wavelength
division multiplexed optical signal; an optical amplifier
configured to amplify the wavelength division multiplexed optical
signal to thereby produce an optically amplified wavelength
division multiplexed optical signal; and transmitter optics
configured to accept the optically amplified wavelength division
multiplexed optical signal and transmit an optical feeder uplink
beam to the satellite in dependence thereon.
17. The subsystem of claim 16, further comprising: a user data to
spot beam controller configured to accept a set of user data
signals and combine subsets of the user data signals into the spot
beam signals that are provided to the GBBF.
18. The subsystem of claim 16, further comprising: a plurality of
frequency up-converters each of which is configured to frequency-up
convert one of the feed element signals output by the GBBF before
the feed element signal is provided to one of the EOMs; and a
plurality of filters each of which is configured to filter one of
the feed element signals after the feed element signal has been
frequency up-converted, but prior to the feed element signal being
provided to one of the EOMs; wherein the frequency up-converters
are configured to cause the the optical feed element signals output
by the plurality of EOMs to each have an RF frequency within a same
specified RF frequency range within which the satellite is
configured to transmit the plurality of RF service downlink
beams.
19. The subsystem of claim 16, wherein a specified RF frequency
range within which the satellite is configured to produce and
transmit the plurality of RF service downlink beams comprises a
downlink portion of the Ka band.
20. The subsystem of claim 16, wherein an optical wavelength range
of the optical feeder uplink beam is a contiguous or non-contiguous
optical wavelength range within an infrared (IR) spectrum.
Description
PRIORITY CLAIM
[0001] This application claims priority to U.S. Provisional Patent
Application No. 62/384,604, filed Sep. 7, 2016, which is
incorporated herein by reference in its entirety.
BACKGROUND
[0002] There is increasing need for large amounts of bandwidth to
be routed between a ground based gateway and a spaced based
satellite. With the recent announcement of planned Ka band and Ku
band satellite constellations, it would be beneficial if such
frequency band satellite constellations can be used to help satisfy
the aforementioned increasing need for large amounts of bandwidth
to be routed between a ground based gateway and a spaced based
satellite.
BRIEF DESCRIPTION OF THE DRAWINGS
[0003] FIG. 1 is a block diagram describing a wireless
communication system, which may be a satellite communication
system.
[0004] FIG. 2A depicts gateway forward link equipment, according to
an embodiment of the present technology.
[0005] FIG. 2B depicts components of the ground based beamformer
(GBBF) introduced in FIG. 2A, according to an embodiment of the
present technology.
[0006] FIG. 3 depicts space segment forward link equipment,
according to an embodiment of the present technology.
[0007] FIG. 4A depicts a portion of space segment return link
equipment, according to alternative embodiments of the present
technology.
[0008] FIG. 4B depicts a further portion of space segment return
link equipment, according to an embodiment of the present
technology.
[0009] FIG. 5A depicts gateway return link equipment, according to
an embodiment of the present technology.
[0010] FIG. 5B depicts components of the ground based beamformer
(GBBF) introduced in FIG. 5A, according to an embodiment of the
present technology.
[0011] FIG. 6 is a high level flow diagram that is used to
summarize methods for enabling a ground based subsystem to produce
and transmit an optical feeder uplink beam to a satellite,
according to certain embodiments of the present technology.
[0012] FIG. 7 is a high level flow diagram that is used to describe
additional details of one of the steps introduced with reference to
FIG. 6, according to certain embodiments of the present
technology.
DETAILED DESCRIPTION
[0013] Certain embodiments of the present technology described
herein relate to system and sub-system architectures for high
throughput satellites (HTS), very high throughput satellites (VHTS)
and very very high throughput satellites (VVHTS), which is also
known as ultra high throughput satellites (UHTS), all of which can
be collectively referred to as HTS. Embodiments of the present
technology can also be used to implement mobile satellite services
(MSS) and direct-to-home (DTH) satellite services. Because of
spectrum availability, if feeder links between gateway (GW) sites
and satellites are at optical frequencies, then the number of GW
sites can be drastically reduced compared to if the feeder links
are at RF frequencies, which leads to significant cost savings in
the space and ground segments. Even with the availability of 5 GHz
spectrum at V band and dual polarization, a satellite with
Terabit/sec (Tb/s) capacity would need between 40 and 70 GWs using
RF feeder links, depending on the spectral efficiency achieved, as
described in a conference paper titled "Optical Feederlinks for
VHTS--System Perspectives", by Mata-Calvo et al. (Conference:
Proceedings of the Ka and Broadband Communications, Navigation and
Earth Observation Conference 2015. Ka Conference 2015, 12-14 Oct.
2015, Bologna, Italy). In contrast, using optical feeder links can
reduce the total active GW count to one (plus a few sites would be
added for diversity and redundancy; but note that V/Q band or Ka
band GWs typically also need diversity and redundancy sites to
achieve high availability).
[0014] Prior to describing details of specific embodiments of the
present technology, it is first useful to describe an exemplary
wireless communication system with which embodiments of the present
technology would be useful. An example of such a wireless
communication system will now be described with reference to FIG.
1.
[0015] FIG. 1 depicts a block diagram of a wireless communications
system that includes a communication platform 100, which may be a
satellite located, for example, at a geostationary or
non-geostationary orbital location. In other embodiments, other
platforms may be used such as an unmanned aerial vehicle (UAV) or
balloon, or even a ship for submerged subscribers. In yet another
embodiment, the subscribers may be air vehicles and the platform
may be a ship or a truck where the "uplink" and "downlink" in the
following paragraphs are reversed in geometric relations. Platform
100 may be communicatively coupled to at least one gateway (GW) 105
and a plurality of subscriber terminals ST (including subscriber
terminals 107). The term subscriber terminals may be used to refer
to a single subscriber terminal or multiple subscriber terminals. A
subscriber terminal ST is adapted for communication with the
wireless communication platform 100, which as noted above, may be a
satellite. Subscriber terminals may include fixed and mobile
subscriber terminals including, but not limited to, a cellular
telephone, a wireless handset, a wireless modem, a data
transceiver, a paging or position determination receiver, or mobile
radio-telephone, or a headend of an isolated local network. A
subscriber terminal may be hand-held, portable (including
vehicle-mounted installations for cars, trucks, boats, trains,
planes, etc.) or fixed as desired. A subscriber terminal may be
referred to as a wireless communication device, a mobile station, a
mobile wireless unit, a user, a subscriber, or a mobile. Where the
communication platform of a wireless communication system is a
satellite, the wireless communication system can be referred to
more specifically as a satellite communication system. For the
remainder of this description, unless stated otherwise, it is
assumed that the communication platform 100 is a satellite.
Accordingly, platform 100 will often be referred to as satellite
100, and the wireless communication system will often be referred
to as a satellite communication system.
[0016] In one embodiment, satellite 100 comprises a bus (e.g.,
spacecraft) and one or more payloads (e.g., the communication
payload). The satellite will also include multiple power sources,
such as batteries, solar panels, and one or more propulsion
systems, for operating the bus and the payload.
[0017] The at least one gateway 105 may be coupled to a network 140
such as, for example, the Internet, terrestrial public switched
telephone network, mobile telephone network, or a private server
network, etc. Gateway 105 and the satellite (or platform) 100
communicate over a feeder beam 102, which has both a feeder uplink
102u and a feeder downlink 102d. In certain embodiments, a feeder
downlink beam 102d is a spot beam to illuminate a region 104 on the
Earth's surface (or another surface). Gateway 105 is located in
region 104 and communicates with satellite 100 via feeder beam 102.
Although a single gateway is shown, some implementations will
include many gateways, such as five, ten, or more. One embodiment
includes only one gateway. Each gateway may utilize its own feeder
beam, although more than one gateway can be positioned within a
feeder beam. In one embodiment, a gateway is located in the same
spot beam as one or more subscriber terminals.
[0018] Subscriber terminals ST and satellite 100 communicate over
service beams, which are also known as user beams. For example,
FIG. 1 shows service beams 106, 110, 114 and 118 for illuminating
regions 108, 112, 116 and 120, respectively. In many embodiments,
the communication system will include more than four service beams
(e.g., sixty, one hundred, etc.). Each of the service beams have an
uplink (106u, 110u, 114u, 118u) and a downlink (106d, 110d, 114d,
118d) for communication between subscriber terminals ST and
satellite 100. Although FIG. 1 only shows two subscriber terminals
within each region 108, 112, 116 and 120, a typical system may have
thousands of subscriber terminals within each region.
[0019] In one embodiment, communication within the system of FIG. 1
follows a nominal roundtrip direction whereby data is received by
gateway 105 from network 140 (e.g., the Internet) and transmitted
over the forward path 101 to a set of subscriber terminals ST. In
one example, communication over the forward path 101 comprises
transmitting the data from gateway 105 to satellite 100 via uplink
102u of feeder beam 102, through a first signal path on satellite
100, and from satellite 100 to one or more subscriber terminals ST
via downlink 106d of service beam 106. An uplink (e.g., 102u) of a
feeder beam (e.g., 102) can also be referred to more succinctly as
a feeder uplink beam, and the downlink (e.g., 106d) of a service
beam (e.g., a 106) can also be referred to more succinctly as a
service downlink beam. Although the above example mentions service
beam 106, the example could have used other service beams.
[0020] Data can also be sent from the subscriber terminals STs over
the return path 103 to gateway 105. In one example, communication
over the return path comprises transmitting the data from a
subscriber terminal (e.g., subscriber terminal 107 in service beam
106) to satellite 100 via uplink 106u of service beam 106, through
a second signal path on satellite 100, and from satellite 100 to
gateway 105 via downlink 102d of feeder beam 102. An uplink (e.g.,
106u) of a service beam (e.g., 106) can also be referred to more
succinctly as a service uplink beam, and the downlink 102d of
feeder beam 102 can also be referred to more succinctly as a feeder
downlink beam. Although the above example uses service beam 106,
the example could have used any service beam.
[0021] FIG. 1 also shows a Network Control Center (NCC) 130, which
can include an antenna and modem for communicating with satellite
100, as well as one or more processors and data storage units.
Network Control Center 130 provides commands to control and operate
satellite 100. Network Control Center 130 may also provide commands
to any of the gateways and/or subscriber terminals.
[0022] FIG. 1 also shows calibration and pointing stations 150 that
are used to determine amplitude and phase errors associated with
forward path and return path signals 101 and 103, which amplitude
and phase errors can be used by a ground based beam former (GBBF)
(e.g., 230 in FIGS. 2A and 2B) to perform ground based beamforming,
in accordance with certain embodiments of the present technology.
More specifically, the amplitude and phase errors can be used as,
or used to determine, amplitude and phase coefficients that are
used by the GBBF 230 to perform ground based beamforming. In
accordance with certain embodiments, the calibration and pointing
stations 150 are part of a calibration subsystem. Such a
calibration subsystem can also include one or more processors and
data storage units. The calibration subsystem can control the
transmission and reception of calibration signals, and can control
the execution of algorithms and/or the like that are used to
determine amplitude and phase errors and/or coefficients. The
calibration subsystem may also be used for forward uplink power
control and to correct for Doppler effects, but is not limited
thereto.
[0023] In one embodiment, communication platform 100 implements the
technology described below. In other embodiments, the technology
described below is implemented on a different platform (or
different type of satellite) in a different communication system.
For examples, the communication platform can alternatively be a UAV
or balloon, but is not limited thereto.
[0024] The architecture of FIG. 1 is provided by way of example and
not limitation. Embodiments of the disclosed technology may be
practiced using numerous alternative implementations.
[0025] Conventionally, a gateway (e.g., gateway 105) communicates
with a satellite (e.g., satellite 100) using an antenna on the
ground that transmits and receives RF (radiofrequency) signals to
and from an antenna on the satellite. Certain embodiments of the
present technology utilize optical components (instead of antennas)
to transmit and receive optical signals (instead of RF signals)
between a gateway and a satellite, as will be described in
additional details below.
[0026] Certain embodiments of the present technology involve the
use of analog-over free-space optical signals, which leads to an
elegant architecture for a satellite repeater, whereby all
frequency down-conversion in the forward link is eliminated. An
advantage of this approach, especially for HTS satellites, is that
it eliminates the need for very high speed Analog-to-Digital
Converters (ADCs) and Digital to Analog Converters (DACs) on the
satellites. Further, this approach allows the aggregation of
multiple user links but does not require extra hardware associated
with an onboard demodulator and remodulator, and thus reduces the
mass, power and cost of the satellite, perhaps making the
difference between being able to launch or not being able to launch
the satellite. In addition, in accordance with specific embodiments
where the uplink and downlink communication signals are modulated
at transmit (forward) and receive (return) RF frequencies, no
frequency conversion in the forward link is required on the
satellite, thereby further simplifying the payload design. By
contrast, previously envisioned free-space optical spacecraft
architectures proposed demodulation of the optical signal, followed
by routing to user link pathways and remodulation of the signal on
user link RF frequencies. Further, certain embodiments of the
present technology eliminate the need for a satellite to include an
onboard channelizer, as will be described in additional detail
below.
[0027] Block diagrams for the communications subsystems for the
ground and space segments, according to certain embodiments of the
present technology, are described below with reference to FIGS. 2A,
2B, 3, 4A, 4B, 5A and 5B. Certain embodiments use analog modulation
and demodulation on the satellite, thus enabling optical feeder
links without onboard processing.
[0028] FIGS. 2A and 2B will first be used to describe gateway
forward link equipment according to certain embodiments of the
present technology. FIG. 3 will then be used to describe space
segment forward link equipment according to an embodiment of the
present technology. In specific embodiments, two hundred and fifty
laser wavelengths are combined at a single gateway (which can be
referred to as an optical gateway) and sent to the satellite, which
has multiple (e.g., two hundred and fifty) user beams (also known
as service beams) operating at Ka band frequencies. In accordance
with an embodiment, each wavelength carries 2.5 GHz so that a total
of 625 GHz is sent from the gateway on the ground to the satellite.
At a modest spectral efficiency of 2 bps/Hz, this leads to a 1.25
Tb/s satellite design. In accordance with another embodiment, each
wavelength carries 2.9 GHz so that a total of 725 GHz is sent from
the gateway on the ground to the satellite. At a modest spectral
efficiency of 2 bps/Hz, this leads to a 1.45 Tb/s satellite design.
FIGS. 4A and 4B and FIGS. 5A and 5B will thereafter be used to
depict return link equipment for a satellite and a gateway.
Gateway Forward Link Equipment
[0029] FIG. 2A will now be used to describe gateway forward link
equipment 200, according to an embodiment of the present
technology. Such gateway forward link equipment 200 can also be
referred to as an optical gateway forward link subsystem 200, or
more generally, as an optical communication subsystem. Referring to
FIG. 2A, the optical gateway forward link subsystem 200 is shown as
including two hundred and fifty lasers 202_1 to 202_250, two
hundred and fifty electro-optical modulator (EOMs) 204_1 to
204_250, a wavelength-division multiplexing (WDM) multiplexer (MUX)
206, an optical amplifier (OA) 208, and transmitter optics 210. The
optical gateway forward link subsystem 200 is also shown as
including a user data to spot beam controller 220 and a ground
based beam former (GBBF) 230. The optical gateway forward link
subsystem 200 is also shown as including two hundred and fifty
local oscillators (LOs) 242_1 to 242_250, two hundred and fifty
frequency up converters (FUCs) 244_1 to 244_250, and two hundred
and fifty filters (FTRs) 246_1 to 246_250. Each of these elements
is described below.
[0030] The user data to spot beam controller 220 is shown as
receiving user data signals, e.g., 10,000 user data signals. An
individual user data signal can be for forwarding to an individual
service terminal ST, or multiple user data signals can be for
simultaneously forwarding to an individual service terminal ST. In
a broadcast scheme, an individual user data signal can be for
forwarding to multiple service terminals ST simultaneously.
Additional and/or alternative variations are also possible. These
user data signals, as will be described below, are included within
an optical feeder uplink beam (e.g., 102u) that is transmitted by
the gateway forward link equipment 200 to a satellite (e.g., 100),
and the satellite includes the user data signals within spot beams
(e.g., the RF service downlink beams 106d, 110d, 114d and 118d in
FIG. 1) that are transmitted to service terminals ST. Assume, for
example, that the satellite (e.g., 100 in FIG. 1) is configured to
transmit one thousand spot beams using two hundred and fifty feed
elements (e.g., feed elements 326_1 to 326_250 in FIG. 3), and that
the user data to spot beam controller 220 receives ten thousand
user data signals. Continuing with this example, the user data to
spot beam controller 220 would map the ten thousand user data
signals to one thousand spot beam signals, which are provided to
the GBBF 230. The one thousand spot beam signals that are provided
to the GBBF 230, will, after they are included within an optical
feeder uplink beam (e.g., 102u) that is transmitted by the gateway
forward link equipment 200 to a satellite (e.g., 100), be used by
the satellite (e.g., 100) to transmit one thousand spot beams that
each cover a limited geographic region on Earth. More generally,
the user data to spot beam controller 220 is configured to map, to
each of a plurality of spot beam signals (e.g., to each of one
thousand spot beam signals), a subset (e.g., .about.ten) of the
plurality of user data signal signals (e.g., ten thousand user data
signals). The user data to spot beam controller 220, in accordance
with certain embodiments, is performed digitally.
[0031] The GBBF 230, as will be described in additional detail with
reference to FIG. 2B, receives the one thousand spot beam signals,
and uses calibration information received from a calibration
subsystem, to produce two hundred and fifty baseband feed element
signals. The two hundred and fifty baseband feed element signals
are provided to respective frequency up-converters (FUCs) 244_1 to
244_250, each of which also receives an RF carrier signal from a
respective one of the local oscillators (LOs) 242_1 to 242_250. In
other words, the local oscillators (LOs) 242_1 to 242_250, which
can be referred to collectively as LOs 242, or individually as an
LO 242, provide RF carrier signals to the FUCs 244, so that the
FUCs 244 can frequency up-convert the feed element signals to a
desired frequency range. In accordance with certain embodiments, in
order to eliminate a need for RF frequency down-converters in the
forward link equipment (e.g., 300 in FIG. 3) onboard the satellite,
the carrier frequencies of the RF signals are used to up convert
the feed element signals to the desired user downlink frequency
band within the Ka band (or some other allotted band). As a result,
the satellite repeater is greatly simplified. Still referring to
FIG. 2A, the two hundred and fifty frequency up-converted feed
elements signals (which can also be referred to more succinctly as
feed element signals) are shown as being filtered by responsive
FTRs 246_1 to 246_2, to filter out unwanted frequency components
(e.g., unwanted mixed products) that result from the frequency
up-conversions.
[0032] For an example, a portion of the Ka band that may be
desirable to use for transmitting service downlink beams (also
referred to as downlink user beams, or spot beams) from satellite
100 to service terminals ST can be from 17.7-20.2 GHz, and thus,
includes a 2.5 GHz bandwidth. In such a case, each of the EOMs 204
could modulate the optical signal it receives (e.g., via an optical
fiber from a respective laser 202) with a separate RF signal having
a frequency within the range from 17.7-20.2 GHz. In other words,
the FUCs 244 can be used to frequency up-convert baseband feed
element signals to be within the frequency range from 17.7-20.2
GHz. Further, since each of the two hundred and fifty optical data
signals (produced by the two hundred and fifty EOMs) has a
bandwidth of 2.5 GHz, the bandwidth of the optical feeder uplink
beam that is sent from the ground to the satellite is 625 GHz
(i.e., 2.5 GHz*250=625 GHz). For another example, a portion of the
Ka band that may be desirable to use for transmitting service
downlink beams (also referred to as downlink user beams or spot
beams) from satellite 100 to service terminals ST can be from
17.3-20.2 GHz, and thus, includes a 2.9 GHz bandwidth. In such a
case, each of the EOMs 204 could modulate the optical signal it
receives (e.g., via an optical fiber from a respective laser 202)
with a separate RF signal having a frequency within the range from
17.3-20.2 GHz. In other words, the FUCs 244 can be used to
frequency up-convert baseband feed element signals to be within the
frequency range from 17.3-20.2 GHz. Further, since each of the two
hundred and fifty optical data signals (produced by the two hundred
and fifty EOMs) has a bandwidth of 2.9 GHz, the bandwidth of the
optical feeder uplink beam that is sent from the ground to the
satellite is 725 GHz (i.e., 2.9 GHz*250=725 GHz).
[0033] Still referring to FIG. 2A, each of the two hundred and
fifty separate EOMs 204_1 to 204_250 is shown as receiving a
respective one of the frequency up-converted feed element signals
and a respective one of a plurality of optical carrier signals
output by the two hundred and fifty lasers 202_1 to 201_250, which
can be referred to individually as a laser 202, or collectively as
the lasers 202. Explained another way, the light emitted by each of
the two hundred and fifty lasers 202, which can be referred to as
an optical carrier signal, is provided (e.g., via a respective
optical fiber) to a respective one of the two hundred and fifty
separate EOMs 204_1 to 204_250.
[0034] The two hundred and fifty separate lasers 202_1 to 202_250
each emit light of a different wavelength within a specified
wavelength range that is for use in producing the optical feeder
uplink beam (e.g., 102u). The lasers as noted above can be referred
to individually as a laser 202, or collectively as the lasers 202.
Where the specified wavelength range is, for example, from 1510
nanometers (nm) to 1560 nm, then the laser 202_1 may emit light
having a peak wavelength of 1510 nm, the laser 202_2 may emit light
having a peak wavelength of 1510.2 nm, the laser 202_3 (not shown)
may emit light having a peak wavelength of 1510.4 nm, . . . the
laser 202_249 (not shown) may emit light having a peak wavelength
of 1559.8 nm, and the laser 202_250 may emit light having a peak
wavelength of 1560 nm. In other words, the peak wavelengths emitted
by the lasers 202 can occur at 0.2 nm intervals from 1510 nm to
1560 nm. The wavelength range from 1510 nm to 1560 nm, which is
within the infrared (IR) spectrum, is practical to use because IR
lasers for use in communications are readily available. However,
wider or narrow wavelength ranges, within the same or other parts
of the optical spectrum, may alternatively be used. For example, it
would also be possible to utilize a wavelength range within the 400
nm-700 nm visible spectrum. It is also possible that the wavelength
range that is specified for use in producing the optical feeder
uplink beam (e.g., 102u) is non-contiguous. For example, the
wavelength range that is for use in producing the optical feeder
uplink beam can be from 1510 nm to 1534.8 nm and from 1540.2 nm to
1564.8 nm. Further, it is also possible that gateway forward link
equipment can alternatively include more or less than two hundred
and fifty lasers (that each emit light of a different peak
wavelength within a specified contiguous or non-contiguous
wavelength range). Additionally, it is noted that the gateway
forward link equipment may include two or more of each of the
lasers (that each emit light of a different peak wavelength within
a specified contiguous or non-contiguous wavelength range) to
provide for redundancy or backup. Each of the lasers 202 can be,
for example, a diode-pumped infrared neodymium laser, although the
use of other types of lasers are also within the scope of the
embodiments described herein.
[0035] To reduce and preferably avoid interference, the wavelength
range that is for use in producing the optical feeder uplink beam
(e.g., 102u) should be different than the wavelength range that is
for use in producing the optical feeder downlink beam (e.g., 102d).
For example, if the wavelength range that is for use in producing
the optical feeder uplink beam 102u is from 1510 nm to 1560 nm,
then the wavelength range that is for use in producing the optical
feeder downlink beam 102d can be from 1560.2 nm to 1575 nm. For
another example, if the wavelength range that is for use in
producing the optical feeder uplink beam 102u is from 1510 nm to
1534.8 nm and from 1540.2 nm to 1564.8 nm, then the wavelength
range that is for use in producing the optical feeder downlink beam
102d can be from 1535 nm to 1540 nm and from 1565 nm to 1575 nm.
These are just a few examples, which are not intended to be all
encompassing. Details of how an optical feeder downlink beam (e.g.,
102d) can be produced in accordance with an embodiment of the
present technology are provided below in the discussion of FIGS. 4A
and 4B.
[0036] Still referring to FIG. 2A, the light emitted by each of the
two hundred and fifty lasers 202, which can be referred to as an
optical carrier signal, is provided (e.g., via a respective optical
fiber) to a respective one of the two hundred and fifty separate
EOMs 204_1 to 204_250. Each of the EOMs is an optical device in
which a signal-controlled element exhibiting an electro-optic
effect is used to modulate a respective beam of light. The
modulation performed by the EOMs 204 may be imposed on the phase,
frequency, amplitude, or polarization of a beam of light, or any
combination thereof. In accordance with a specific embodiment, each
of the EOMs 204 is a phase modulating EOM that is used as an
amplitude modulator by using a Mach-Zehnder interferometer. In
other words, each of the EOMs 204 can be implemented as a
Mach-Zehnder modulator (MZM), which can be a Lithium Niobate
Mach-Zehnder modulator, but is not limited thereto. In accordance
with specific embodiments, each of the EOMs 204 is implemented as
an MZM that produces an amplitude modulated (AM) optical waveform
with a modulation index between 10% and 80% in order to maintain
fidelity of an RF waveform (modulated therein) without too much
distortion. The optical signal that is output by each of the EOMs
204 can be referred to as an optical frequency up-converted feed
element signal, or more succinctly as an optical feed element
signal. The modulation scheme that is implemented by the EOMs 204
can result in double- or vestigial-sidebands, including both an
upper sideband (USB) and a lower sideband (LSB). Alternatively
single-sideband modulation (SSB) can be utilized to increase
bandwidth and transmission power efficiency.
[0037] The two hundred and fifty separate optical feed element
signals that are output by the two hundred and fifty EOMs 204 are
provided to the WDM MUX 206, which can also be referred to as a
dense wavelength division multiplexing (DWDM) MUX. The WMD MUX 206
multiplexes (i.e., combines) the two hundred and fifty optical feed
element signals, received from the two hundred and fifty EOMs 204,
onto a single optical fiber, with each of the two hundred and fifty
separate optical feed element signals being carried at the same
time on its own separate optical wavelength within the range from
1510 nm to 1560 nm (or some other contiguous or non-contiguous
wavelength range). For example, as explained above, the two hundred
and fifty separate optical feed element signals can have peak
wavelengths of 1510 nm, 1510.2 nm, 1510.4 nm . . . 1559.8 nm and
1560 nm.
[0038] The signal that is output by the WMD MUX 206, which can be
referred to as a wavelength division multiplexed optical signal, is
provided to the optical amplifier (OA) 208. The OA 208 amplifies
the wavelength division multiplexed optical signal so that the
wavelength division multiplexed optical signal has sufficient power
to enable transmission thereof from the ground to the satellite 100
in space. An exemplary type of OA 208 that can be used is an
erbium-doped fiber amplifier (EDFA). However embodiments of the
present technology are not limited to use with an EDFA. The output
of the OA 208 can be referred to as an optically amplified
wavelength division multiplexed optical signal.
[0039] The optically amplified wavelength division multiplexed
optical signal, which is output by the OA 208, is provided (e.g.,
via an optical fiber) to the transmitter optics 210. The
transmitter optics 210, which can also be referred to as a
telescope, can includes optical elements such as lenses, mirrors,
reflectors, filters and/or the like. The transmitter optics 210
outputs a collimated optical feeder uplink beam that is aimed at a
satellite. A gimbal, and/or the like, can be used to control the
steering of the transmitter optics 210. In accordance with an
embodiment, the collimated optical feeder uplink beam has an
aperture of about 100 cm, and a half beam divergence of about
0.0000004 radians, wherein the term "about" as used herein means
+/-10 percent of a specified value. The use of other apertures and
half beam divergence values are also within the scope of the
embodiments described herein. The collimated optical feeder uplink
beam, which is output by the transmitter optics 210, is transmitted
in free-space to receiver optics on a satellite. The term
"free-space" means air, outer space, vacuum, or something similar
(which is in contrast to using solids such as optical fiber cable,
an optical waveguide or an optical transmission line). Reception
and processing of the optical feeder uplink beam received at the
satellite will be described in additional detail below. However,
before describing the reception and processing of the optical
feeder uplink beam received at the satellite, additional details of
the gateway forward link equipment, according to certain
embodiments of the present technology, will first be provided.
[0040] In order to wavelength division multiplex two hundred and
fifty wavelengths produced by the two hundred and fifty lasers
202_1 to 202_250, a combination of C band optical frequencies (from
1530 nm to 1565 nm) and L band optical frequencies (from 1565 nm to
1625 nm) may be used, in order to keep the separation of the
wavelengths to be at least 20-25 GHz in order to reduce and
preferably minimize inter-wavelength interference that may occur in
an optical fiber due to non-linearities. If fewer wavelengths are
used (e.g., at C band alone), and higher bandwidth is available at
Ka band per user beam (e.g., if 2.9 GHz is available as it is in
certain ITU Regions), the overall throughput still remains of the
order of several hundred GHz, which lets the capacity reach the
Tb/s range. If instead each wavelength carries more than the Ka
band user bandwidth, fewer wavelengths can be used, but some amount
of frequency conversion may be needed in the space segment forward
link equipment.
[0041] A technology that is increasingly being deployed for use
with satellite communication is ground based beamforming, where a
feederlink is segmented into smaller frequency bands and routed to
different feeds that then form beams as needed using ground based
beamforming in a dynamic manner, which allows flexibility to meet
changing an evolving traffic demands. However, at high frequencies
(such as Ku band or Ka band) ground based beamforming typically
requires a large number of feeds to form good quality beams and the
per-feed bandwidth multiplied by the number of feeds gets too large
for any RF spectrum to handle. For this reason, ground based
beamforming has been limited to mobile-satellite service (MSS)
systems where per-beam bandwidth is limited and the number of feed
elements is also small.
[0042] Embodiments of the present technology use analog over free
space optics (AoFSO) technology to generate the feeder links from a
gateway to/from a satellite, thereby using optical signals to
replace the normal Ku or Ka or V band RF spectrum. By modulating
these optical wavelengths at the desired RF frequencies, it is
possible to use ground based beamforming, even at high frequencies
like Ka band, and with large numbers of feed elements, due to the
high RF bandwidth available at optical frequencies.
[0043] Beneficially, with ground based beamforming, spot beams can
be added, removed or reconfigured within a gateway to enable a
satellite to operate from different orbital locations and to adapt
to changes in traffic patterns or to new applications.
[0044] FIG. 2B will now be used to provided details of the GBBF 230
introduced in FIG. 2A, according to certain embodiments of the
present technology. Referring to FIG. 2B, the GBBF 230 is shown as
including a GBBF controller 232 and one thousand 1 to N splitters
234_1 to 234_1000, where N can equal, e.g., two hundred and fifty,
but is not limited thereto. Each individual splitter 234_1 to
234_1000 (which can be referred to collectively as the splitters
234, or individually as a splitter 234) outputs N copies of the
spot beam signal received by the splitter 234. For example, the
splitter 234_1, which receives the spot beam signal_1, outputs N
copies of the spot beam signal_1. The N outputs of each of the
splitters 234, are provided to respective phase and amplitude
weight elements 236, which can be implemented in hardware, but are
more likely implemented in software and/or firmware. In accordance
with certain embodiments, the function of the splitters 234 is
performed using a digital signal processor (DSP) instead of N
separate splitters. In other words, a DSP can perform the signal
copying or replication. An output of each of the phase and
amplitude weight elements 236 is provided to one of the two hundred
and fifty summers 238_1 to 238_250. The outputs of the summers
238_1 to 238_250 are the baseband feed element signals that are
frequency up-converted by the FUCs 244, filtered by the filters
246, and then provided to the EOMs 204, as shown in FIG. 2A, which
was discussed above. The GBBF 230 can be implemented entirely in
software. Alternatively, or additionally, the GBBF 230 can be
implemented in hardware and/or firmware. The outputs of the phase
and amplitude weight elements 236 can be referred to a component
element signals. The outputs of the summers 238, which outputs are
referred to as the baseband feed element signals above, can also be
referred to as composite signals, since they are a composite of a
plurality of component element signals. In the manner described
above, these composite signals are frequency up-converted,
filtered, electro-optically modulated, WDM multiplexed, amplified
and optically transmitted to a satellite.
[0045] The splitters 234 and the weight elements 236 can be
collectively referred to as a signal replication and forward
beamforming weighting unit 233. Assuming there are one thousand
spot beam signals provided to the signal replication and forward
beamforming weighting unit 233, and two hundred and fifty feed
elements on a satellite (to which the gateway forward link
equipment 200 is transmitting a feeder uplink beam, e.g., 102u),
then the GBBF controller 232 uses calibration signals (received
from a calibration subsystem) to derive element specific amplitude
and phase corrections that are applied individually to two hundred
and fifty thousand component element signals (i.e., one thousand
spot beam signals*two hundred and fifty feed elements=two hundred
and fifty thousand component element signals). As noted above, a
DSP can perform the signal copying or replication performed by the
splitters 234. More generally, all of the functions of the elements
described within the block labeled GBBF 230 can be implemented by a
DSP. In other words, the GBBF 230 can be entirely or substantially
entirely implemented using a DSP. Nevertheless, it is useful to
shown and describe the elements shown in FIG. 2B in order to
understand the operation of such a DSP.
[0046] The calibration subsystem from which the the GBBF controller
232 receives calibration signals can transmit and/or receive
calibration signals upon which calibration measurements can be
performed. These forward and return link measurements can be
generally referred to as a beamforming calibration process, and can
be used to initialize, update and refine the performance of RF
service downlink beams (e.g., 106d, 110d, 114d and 118d in FIG. 1)
and RF service uplink beams (e.g., 106u, 110u, 114u, 118u in FIG.
1). The calibration and pointing stations 150 in FIG. 1 can be part
of such a calibration subsystem. To form a specific beam, the
amplitude and phase weightings should be set to the appropriate
values for each feed element, and should be effectively applied at
the feed element apertures. For example, take two feed elements and
assume a desired beam is formed with an amplitude of A1 and a phase
of .theta.1 degrees for feed element one and an amplitude of A2 and
a phase of .varies.2 degrees for feed element two. In typical on
board beamforming the beam forming operation is very close to the
feed aperture, so it is much simpler to set these values correctly.
However, with ground based beamforming, the signals traverse down
independent paths, through the propagation media at different
frequencies which may have differing amplitude and phase channels,
and then through independent conversion paths. One of the paths may
experience more amplitude attenuation and phase shift than the
other. Without knowledge and compensation of this difference, the
beam forming weights at the aperture will not be the desired
values. Depending on the error experienced, the desired beam may be
mispointed, misshaped, or even dispersed so grossly as to not be
recognizable as a spot beam. However, if the value of the amplitude
and phase difference between the element paths between the feed
element aperture and the ground based beamforming operation is
known, it is relatively simply to be compensated for by adjusting
the feed coefficient weights or compensating for the shift before
applying the feed weights. Consequently, in order for the GBBF 230
to function properly a calibration scheme can be used by a
calibration subsystem to determine and compensate for the amplitude
and phase variations between the feed element paths. Examples of
such calibration subsystems and schemes for use with ground based
beamforming are described in U.S. Pat. No. 7,787,819 to Walker et
al., entitled "Ground-Based Beamforming for Satellite
Communications Systems" and in an article entitled "Architecture,
Implementation and Performance of Ground-Based Beam Forming in the
DBSD G1 Mobile Satellite System" by Walker et al. (28th AIAA
International Communications Satellite Systems Conference
(ICSSC-2010)), each of which is incorporated herein by
reference.
Space Segment Forward Link Equipment
[0047] FIG. 3 will now be used to describe space segment forward
link equipment 300 according to an embodiment of the present
technology. Such space segment forward link equipment 300, which
can also be referred to as a forward link satellite subsystem 300,
or more generally, as an optical communication subsystem, is
configured to receive the optical signal that is transmitted from
the ground based optical gateway subsystem 200 to the satellite
that is carrying the space segment forward link equipment 300. The
space segment forward link equipment 300 is also configured to
convert the optical signal that it receives (from the ground based
optical gateway subsystem 200) into electrical signals, and to
produce service beams therefrom, wherein the service beams are for
transmission from the satellite to service terminals ST.
[0048] Referring to FIG. 3, the forward link satellite subsystem
300 is shown as including receiver optics 302, an optical amplifier
(OA) 304, a wavelength-division multiplexing (WDM) demultiplexer
(DEMUX) 306, two hundred and fifty photodetectors (PDs) 308_1 to
308_250, two hundred and fifty filters 310_1 to 310_250, and two
hundred and fifty low noise amplifiers (LNAs) 312_1 to 312_250. The
forward link satellite subsystem 300 is also shown as including two
hundred and fifty filters (FTRs) 316_1 to 316_250, high power
amplifiers (HPAs) 318_1 to 318_250, harmonic filters (HFs) 320_1 to
320_250, test couplers (TCs) 322_1 to 322_250, orthomode junctions
(OMJs) 324_1 to 324_250, and feed elements 326_1 to 326_250. The
PDs 308_1 to 308_250 can be referred to individually as a PD 308,
or collectively as the PDs 308. The filters 310_1 to 310_250 can be
referred to individually as a filter 310, or collectively as the
filters 310. The LNAs 312_1 to 312_250 can be referred to
individually as an LNA 312, or collectively as the LNAs 312. The
filters 316_1 to 316_250 can be referred to individually as a
filter 316, or collectively as the filters 316. The HPAs 318_1 to
318_250 can be referred to individually as an HPA 318, or
collectively as the HPAs 318. The HFs 320_1 to 320_250 can be
referred to individually as an HF 320, or collectively as the HFs
320. The TCs 322_1 to 322_250 can be referred to individually as a
TC 322, or collectively as the TCs 322. The OMJs 324_1 to 324_250
can be referred to individually as an OMJ 324, or collectively as
the OMJs 324. The feed elements 326_1 to 326_250 can be referred to
individually as a feed element 326, or collectively as the feed
elements 326.
[0049] The receiver optics 302, which can also be referred to as a
telescope, can includes optical elements such as mirrors,
reflectors, filters and/or the like. The receiver optics 302
receives the optical feeder uplink beam that is transmitted through
free-space to the satellite by the ground based optical gateway
forward link subsystem 200, and provides the received optical
feeder uplink beam (e.g., via an optical fiber) to the OA 304. A
gimbal, and/or the like, can be used to control the steering of the
receiver optics 302. When the optical feeder uplink beam reaches
the satellite, the power of the optical feeder uplink beam is
significantly attenuated compared to when it was transmitted by the
ground based optical gateway subsystem 200. Accordingly, the OA 304
is used to amplify the received optical feeder uplink beam before
it is provided to the WDM DEMUX 306. The OA 304 can be, e.g., an
erbium-doped fiber amplifier (EDFA), but is not limited thereto.
The output of the OA 304 can be referred to as an optically
amplified received optical feeder uplink beam. The WDM DEMUX 306
demultiplexes (i.e., separates) the received optical feeder uplink
beam (after it has been optically amplified) into two hundred and
fifty separate optical signals, each of which is provided to a
separate photodetector (PD) 308. Each PD 308 converts the optical
signal it receives from the WDM DEMUX 306 to a respective RF
electrical signal. The RF electrical signal produced by each PD 308
is provided to a respective filter (FTR) 310 (e.g., a bandpass
filter) to remove unwanted frequency components and/or enhance
desired frequency components. For an example, each filter 310 can
pass frequencies within the range of 17.7-20.2 GHz, or within the
range of 17.3-20.2 GHz, but are not limited thereto. The filtered
RF electrical signal, which is output by each filter 310, is
provided to a respective low noise amplifier (LNA) 312. Each LNA
312 amplifies the relatively low-power RF signal it receives from a
respective filter 310 without significantly degrading the signals
signal-to-noise ratio. The amplified RF signal that is output by
each LNA 312 is provided to a filter 316. The filter 316_1 may have
a passband of 17.7-20.2 GHz, or 17.3-20.2 GHz, but are not limited
thereto.
[0050] Each HPA 318 amplifies the RF signal it receives so that the
RF signal has sufficient power to enable transmission thereof from
the satellite 100 in space to a service terminal ST, which may be
on the ground. Each HPA 318 can be, e.g., a linearized traveling
wave tube high power amplifier, but is not limited thereto. The
signal that is output by each of the HPAs 318 can be referred to as
an amplified RF signal. Each HF 320 is used to reduce out-of-band
emissions caused by the nonlinearity caused by a respective HPA
318. Each HF 320 can be, e.g., a waveguide cavity filter, but is
not limited thereto. Each test coupler TC 322 can be used for power
monitoring, payload testing and/or performing calibrations based on
signals passing therethrough. Each OMJ 324 adds either right hand
circular polarization (RHCP) or left hand circular polarization
(LHCP) to the RF signal that is passed through the OMJ. This allows
for color reuse frequency band allocation, wherein each color
represents a unique combination of a frequency band and an antenna
polarization. This way a pair of feeder beams that illuminate
adjacent regions can utilize a same RF frequency band, so long as
they have orthogonal polarizations. Alternatively, each OMJ 324
adds either horizontal linear polarization or vertical linear
polarization to the RF signal that is passed through the OMJ. Each
feed element 326, which is an example of a feed element, converts
the RF signal it receives, from a respective OMJ 324, to radio
waves and feeds them to the rest of the antenna system (not shown)
to focus the signal into a service downlink beam. A feed element
326 and the rest of an antenna can be collectively referred to as
the antenna subsystem. All or some of the feed elements 326 can
share a common reflector. Such reflector(s) is/are not shown in the
Figures, to simply the Figures. The two hundred and fifty feed
elements, element 326_1 to 326_250, form a multiple element antenna
feed array. This multiple element antenna feed array is used to
form spot beams (e.g., one thousand spot beams) as controlled by
the GBBF 230.
Space Segment Return Link Equipment
[0051] FIG. 4A will now be used to describe a portion of space
segment return link equipment 400A, according to an embodiment of
the present technology. Such space segment return link equipment
400A, which can also be referred to as a satellite return link
subsystem 400A, or more generally, as an optical communication
subsystem, is configured to receive the RF signals that are
transmitted by service terminals ST to the satellite (e.g., 100)
that is carrying the space segment return link equipment 400A. The
space segment return link equipment 400A, together with the space
segment return link equipment 400B in FIG. 4B, is also configured
to convert the RF signals that it receives (from the service
terminals ST) into optical signals, and to produce optical return
feeder beams therefrom, wherein the optical return feeder beams are
for transmission from the satellite (e.g., 100) to a ground based
gateway (e.g., 105).
[0052] Referring to FIG. 4A, the portion of the space segment
return link equipment 400A shown therein includes feed elements
402_1 to 402_250 (which can be referred to individually as a feed
element 402, or collectively as the feed elements 402), orthomode
junctions (OMJs) 404_1 to 404_250 (which can be referred to
individually as an OMJ 404, or collectively as the OMJs 404), test
couplers (TCs) 406_1 to 406_250 (which can be referred to
individually as a TC 406, or collectively as the TCs 406),
pre-select filters (PFs) 408_1 to 408_250 (which can be referred to
individually as a PF 408, or collectively as the PFs 408), low
noise amplifiers (LNAs) 410_1 to 410_250 (which can be referred to
individually as an LNA 410, or collectively as the LNAs 410), and
filters (FTRs) 412_1 to 412_250 (which can be referred to
individually as a filter 412, or collectively as the filters 412).
The portion of the space segment return link equipment 400A shown
in FIG. 4A also includes frequency down-converters (FDCs) 416_1 to
416_250 (which can be referred to individually as a frequency
down-converter 416, or collectively as the frequency
down-converters 416), filters (FTRs) 418_1 to 418_250 (which can be
referred to individually as a filter 418, or collectively as the
filters 418), and local oscillators (LOs) 422_1 to 422_10 (which
can be referred to individually as an LO 422, or collectively as
the LOs 422). The portion of the space segment return link
equipment 400A shown in FIG. 4A also includes combiners 420_1 to
420_25 (which can be referred to individually as a combiner 420, or
collectively as the combiners 420).
[0053] Each feed element 402 gathers and focuses radio waves of a
service uplink beam (e.g., 106u) and converts them to an RF signal
that is provided to a respective OMJ 404. A feed element 402 and
the rest of an antenna can be collectively referred to as the
antenna or antenna system. In other words, an antenna, as the term
is used herein, can include a feed element. All or some of the feed
elements 402 can share a common reflector. Such reflector(s) is/are
not shown in the Figures, to simply the Figures. Each OMJ 404
either passes through a right hand circular polarization (RHCP) or
a left hand circular polarization (LHCP) RF signal. Each OMJ 404
can alternatively pass through either a horizontal or a vertical
linear polarization RF signal. Each test coupler TC 406 can be used
for power monitoring, payload testing and/or performing
calibrations based on signals passing therethrough. Each pre-select
filter (PF) 408 (e.g., a bandpass filter) is used to remove
unwanted frequency components and/or enhance desired frequency
components. For an example, each PF 408 can pass frequencies within
the range of 29.5-30.0 GHz, but is not limited thereto. Each LNA
410 amplifies the relatively low-power RF signal it receives from a
respective PF 408 without significantly degrading the signals
signal-to-noise ratio. The amplified RF signal that is output by
each LNA 410 is provided to a respective filter 412.
[0054] Each filter 412 allows frequencies to pass within a
specified frequency range (e.g., 29.50-30.00 GHz), and the filters
418 that are downstream of the frequency down-converters 416 are
used to filter out unwanted frequency components (e.g., unwanted
mixed products) that result from the frequency
down-conversions.
[0055] Each frequency down-converter 416 receives an RF signal from
a filter 412 (which RF signal includes data from a uplink beam, and
thus, can be referred to as an RF data signal) and an RF signal
from an LO 422 (which can be referred to as an LO signal), and uses
the LO signal to down-convert the RF data signal to a frequency
range (e.g., 6.70-7.2 GHz, or 6.3-7.2 GHz, or some other frequency
range within the 6-12 GHz band) that can be used for transmitting
feeder downlink signals (e.g., 102d) to a gateway (e.g., 105). The
output of each frequency down- converter 416 is provided to a
filter 418. For example, the frequency down-converter 416_1
provides its output to the filter 418_1, and the frequency
down-converter 416_2 provides its output to the filter 418_2. The
filter 418_1 can be a bandpass filter that allows frequencies to
pass within a specified frequency range (e.g., 6.70-7.2 GHz, or
6.3-7.2 GHz, or some other frequency range within the 6-12 GHz
band).
[0056] In the embodiment of FIG. 4A, the outputs of ten filters 418
are provided to a combiner 420. For example, the outputs of filters
418_1, 418_2, 418_3 . . . 418_10 are provided the combiner 420_1.
Each combiner 420 combines the ten down-converted and filtered
signals it receives into a combined signal that includes data
modulated RF carriers for ten service uplink beams. In other words,
the output of each combiner 420 includes data received from ten
service uplink beams associated with at least ten service terminals
ST. The output of each combiner 420 is provided to a separate EOM
434, as will be discussed below with reference to FIG. 4B.
[0057] FIG. 4B will now be used to describe a further portion of
the space segment return link equipment 400B that is used to
convert the data modulated RF carrier signals into a collimated
optical downlink feeder beam that is aimed at a gateway. Referring
to FIG. 4B, the portion of the space segment return link equipment
400B is shown as including twenty five lasers 432_1 to 432_25,
twenty five electro-optical modulator (EOMs) 434_1 to 434_25, a
wavelength-division multiplexing (WDM) multiplexer (MUX) 436, an
optical amplifier (OA) 438 and transmitter optics 440. Each of
these elements are described below.
[0058] The twenty five separate lasers 432_1 to 432_25 each emit
light of a different wavelength within a specified wavelength
range. The lasers can be referred to individually as a laser 432,
or collectively as the lasers 432. Where the specified wavelength
range is, for example, from 1560 nm to 1570 nm, then the laser
432_1 may emit light having a peak wavelength of 1560 nm, the laser
432_2 may emit light having a peak wavelength of 1560.4 nm, the
laser 432_3 (not shown) may emit light having a peak wavelength of
1560.8 nm, . . . the laser 432_24 may emit light having a peak
wavelength of 1669.6 nm, and the laser 432_25 may emit light having
a peak wavelength of 1670.0 nm. In other words, the peak
wavelengths emitted by the lasers 432 can occur at 0.4 nm intervals
from 1560 nm to 1570 nm. The wavelength range from 1560 nm to 1570
nm, which is within the IR spectrum, is practical to use because IR
lasers for use in communications are readily available. However,
wider or narrow wavelength ranges, within the same or other parts
of the optical spectrum, may alternatively be used. For example, it
would also be possible to utilize a wavelength range within the 400
nm-700 nm visible spectrum. It is also possible that the wavelength
range that is specified for use in producing the optical feeder
downlink beam (e.g., 102d) is non-contiguous. For example, the
wavelength range that is for use in producing the optical feeder
downlink beam can be from 1535 nm to 1540 nm and from 1565 nm to
1575 nm. These are just a few examples, which are not intended to
be all encompassing. Further, it is also possible that space
segment return link equipment can alternatively include more or
less than twenty five lasers (that each emit light of a different
peak wavelength within a specified contiguous or non-contiguous
wavelength range). Additionally, it is noted that the space segment
return link equipment may include two or more of each of the lasers
(that each emit light of a different peak wavelength within a
specified contiguous or non-contiguous wavelength range) to provide
for redundancy or backup. Each of the lasers 432 can be, for
example, a diode-pumped infrared neodymium laser, although the use
of other types of lasers are also within the scope of the
embodiments described herein.
[0059] In accordance with certain embodiments, the space segment
return link equipment 400B includes less lasers (e.g., twenty five
lasers 432) for use in generating the optical feeder downlink beam
that is aimed from the satellite 100 to the gateway 105, than the
gateway forward link equipment 200 includes (e.g., two hundred and
twenty five lasers 202) for generating the optical feeder uplink
beam that is aimed from the gateway 105 to the satellite 100. This
is made possible due to current asymmetric capacity requirements
between the forward and return feeder links. More specifically, a
feeder downlink beam (e.g., 102d) carries significantly less data
than a feeder uplink beam (e.g., 102u), because service terminals
ST typically download much more data than they upload.
[0060] On the return link, given the current asymmetric capacity
requirements between the forward and return links, the space
segment return link equipment can be implemented to handle less
demand that the ground based forward link equipment. As an example,
if each RF service uplink beam is assumed to have only 320 MHz per
beam, then a total of 160 GHz needs to be sent from a satellite to
a gateway on the optical feeder downlink beam. Several beams'
frequencies can be grouped together to create a 4 GHz bandwidth
which is then transmitted on each of twenty five laser wavelengths
that are multiplexed together and transmitted to the ground. An
alternative implementation would be to aggregate the 4 GHz spectrum
with filtering post LNA to eliminate the RF frequency conversion
and as above directly modulate the RF spectrum on each of the
twenty five laser wavelengths. An alternative implementation would
be to use only RF LNAs for each feed, modulate each 320 MHz segment
of bandwidth onto a single laser and combine two hundred and twenty
five laser wavelengths together, thus eliminating the need for RF
frequency converters. Depending on the number of service beams and
feeder beams required, one or the other configuration can be
selected to provide the lowest mass solution.
[0061] The light emitted by each of the twenty five lasers 432,
which can be referred to as an optical carrier signal, is provided
(e.g., via a respective optical fiber) to a respective one of the
twenty five separate EOMs 434_1 to 434_25. The EOMs can be referred
to individually as an EOM 434, or collectively as the EOMs 434.
Each of the EOMs 434 is an optical device in which a
signal-controlled element exhibiting an electro-optic effect is
used to modulate a respective beam of light. The modulation
performed by the EOMs 434 may be imposed on the phase, frequency,
amplitude, or polarization of a beam of light, or any combination
thereof. In accordance with a specific embodiment, each of the EOMs
434 is a phase modulating EOM that is used as an amplitude
modulator by using a Mach-Zehnder interferometer. In other words,
each of the EOMs 434 can be implemented as a Mach-Zehnder modulator
(MZM), which can be a Lithium Niobate Mach-Zehnder modulator, but
is not limited thereto. In accordance with specific embodiments,
each of the EOMs 434 is implemented as an MZM that produces an
amplitude modulated (AM) optical waveform with a modulation index
between 10% and 80% in order to maintain fidelity of an RF waveform
(modulated therein) without too much distortion. The optical signal
that is output by each of the EOMs 434 can be referred to as an
optical data signal. The modulation scheme that is implemented by
the EOMs 434 can result in double- or vestigial-sidebands,
including both an upper sideband (USB) and a lower sideband (LSB).
Alternatively single-sideband modulation (SSB) can be utilized to
increase bandwidth and transmission power efficiency.
[0062] The twenty five separate optical data signals that are
output by the fifty EOMs 434 are provided to the WDM MUX 436, which
can also be referred to as a dense wavelength division multiplexing
(DWDM) MUX. The WMD MUX 436 multiplexes (i.e., combines) the twenty
five optical data signals, received from the twenty five EOMs 434,
onto a single optical fiber, with each of the twenty five separate
optical data signals being carried at the same time on its own
separate optical wavelength within a specified contiguous
wavelength range (e.g., from 1560 nm to 1570 nm) or non-contiguous
wavelength range (e.g., from 1510 nm to 1535 nm, and from 1540 nm
to 1565 nm). For example, as explained above, the twenty five
optical data signals can have peak wavelengths that occur at 0.4 nm
intervals from 1560 nm to 1570 nm, but are not limited thereto.
[0063] The signal that is output by the WMD MUX 436, which can be
referred to as a wavelength division multiplexed optical signal, is
provided to the optical amplifier (OA) 438. The OA 438 amplifies
the wavelength division multiplexed optical signal so that the
wavelength division multiplexed optical signal has sufficient power
to enable transmission thereof from the satellite 100 in free-space
to the gateway 105. The OA 438 can be an erbium-doped fiber
amplifier (EDFA), but is not limited thereto. The output of the OA
438 can be referred to as an optically amplified wavelength
division multiplexed optical signal.
[0064] The optically amplified wavelength division multiplexed
optical signal, which is output by the OA 438, is provided (e.g.,
via an optical fiber) to the transmitter optics 440. The
transmitter optics 440, which can also be referred to as a
telescope, can includes optical elements such as lenses, mirrors,
reflectors, filters and/or the like. The transmitter optics 440
outputs a collimated optical feeder downlink beam that is aimed at
a satellite. A gimbal, and/or the like, can be used to control the
steering of the transmitter optics 440. In accordance with an
embodiment, the collimated optical feeder downlink beam has an
aperture of about 40 cm, and a half beam divergence of about
0.0000012 radians, wherein the term "about" as used herein means
+/-10 percent of a specified value. The use of other apertures and
half beam divergence values are also within the scope of the
embodiments described herein. The collimated optical feeder
downlink beam, which is output by the transmitter optics 440, is
transmitted in free-space to receiver optics in the gateway
105.
[0065] A space segment (e.g., a satellite 100) can have different
optics that are used for transmitting an optical feeder downlink
beam (e.g., 102d) to a gateway, than the optics that are used for
receiving an optical feeder uplink beam (e.g., 102u) from a
gateway. Alternatively, and preferably, to reduce the weight that
needs to be carried by the space segment (e.g., a satellite 100),
the same optics can be used for both transmitting an optical feeder
downlink beam (e.g., 102d) to a gateway and for receiving an
optical feeder uplink beam (e.g., 102u) from a gateway. More
specifically, the TX optics 440 shown in FIG. 4B can be the same as
the RX optics 302 shown in FIG. 3. Additional and/or alternative
components can be shared between the space segment forward link
equipment shown in FIG. 3 and the space segment return link
equipment shown in FIGS. 4A and 4B. For example, the feed elements
326 in FIG. 3 can be the same as the feed elements 402 shown in
FIG. 4A. For another example, the OMJs 324 in FIG. 3 can be the
same as the OMJs 404 in FIG. 4A, if the OMJs are implement as a
three-port device. These are just a few example, which are not
intended to be all encompassing.
[0066] Referring again to the EOMs 434 in FIG. 4B, in accordance
with certain embodiments of the present technology, each of the
EOMs 434 modulates the optical signal it receives (e.g., via an
optical fiber from a respective laser 432) with a separate RF
signal that has already been modulated to include user data. For
example, the EOM 434_1 modulates the optical signal it receives
from the laser 431_1 with a data modulated RF carrier signal it
receives from the combiner 420_1 (in FIG. 4A). The data modulated
RF carrier signal that the EOM 434_1 receives from a combiner
(420_1 in FIG. 4A) can include data corresponding to ten service
uplink beams received from service terminals ST. Similarly, the
EOMs 434_2 to 434_50 can each receive a different data modulated RF
carrier signal, from a different combiner 420, with each data
modulated RF carrier signal corresponding to a different group of
ten service uplink beams received from service terminals ST. In
this manner, the EOMs 434 can be collectively provided with data
modulated RF carrier signals corresponding to two hundred and fifty
service uplink beams (i.e., 25*10=250).
Gateway Return Link Equipment
[0067] FIG. 5A will now be used to describe gateway return link
equipment 500, according to an embodiment of the present
technology. Such gateway return link equipment 500 can also be
referred to as an optical gateway return link subsystem 500, or
more generally, as an optical communication subsystem. Referring to
FIG. 5A, the optical gateway return link subsystem 500 is shown as
including receiver optics 502, an optical amplifier (OA) 504, a
wavelength-division multiplexing (WDM) demultiplexer (DEMUX) 506,
twenty five photodetectors (PDs) 508_1 to 508_25, twenty five
filters (FTRs) 510_1 to 510_25, twenty five low noise amplifiers
(LNAs) 512_1 to 512_25, and twenty five frequency down-converters
(FDCs) 514_1 to 514_25. The optical gateway return link subsystem
500 is also shown as including a ground based beamformer (GBBF)
515, M demodulator and digital signal processor (DSP) blocks 516_1
to 516_M, and twenty five local oscillators (LOs) 522_1 to 522_25
(which can be referred to individually as an LO 522, or
collectively as the LOs 522).
[0068] The receiver optics 502, which can also be referred to as a
telescope, can includes optical elements such as mirrors,
reflectors, filters and/or the like. The receiver optics 502
receives the optical feeder downlink beam (e.g., 102d) that is
transmitted through free-space from a space segment (e.g., a
satellite 100), by the space based return link subsystem 400A and
400B, and provides the received optical feeder downlink beam (e.g.,
via an optical fiber) to the OA 504. A gimbal, and/or the like, can
be used to control the steering of the receiver optics 502. When
the optical feeder downlink beam reaches the gateway, the power of
the optical feeder downlink beam is significantly attenuated
compared to when it was transmitted by the space based return link
subsystem. Accordingly, the OA 504 is used to amplify the received
optical feeder downlink beam before it is provided to the WDM DEMUX
506. The OA 504 can be, e.g., an erbium-doped fiber amplifier
(EDFA), but is not limited thereto. The output of the OA 504 can be
referred to as an optically amplified received optical feeder
downlink beam. The WDM DEMUX 506 demultiplexes (i.e., separates)
the received optical feeder uplink beam (after it has been
optically amplified) into fifty separate optical signals, each of
which is provided to a separate photodetector (PD) 508. Each PD 508
converts the optical signal it receives from the WDM DEMUX 506 to a
respective RF electrical signal. The RF electrical signal produced
by each PD 508 is provided to a respective filter (FTR) 510 (e.g.,
a bandpass filter) to remove unwanted frequency components and/or
enhance desired frequency components. For an example, where
frequency down-conversions were performed on the satellite (by the
FDCs 416 of the space segment return link equipment 400A), each
filter 510 can pass frequencies within the range of 6.70-7.2 GHz,
or within the range of 6.3-7.2 GHz, but are not limited thereto.
For another example, where frequency down-conversions were not
performed on the satellite, each filter 510 can pass frequencies
within the range of 29.5-30 GHz, but are not limited thereto. The
filtered RF electrical signal, which is output by each filter 408,
is provided to a respective low noise amplifier (LNA) 512. Each LNA
512 amplifies the relatively low-power RF signal it receives from a
respective filter 510 without significantly degrading the signals
signal-to-noise ratio. The amplified RF signal that is output by
each LNA 512 is provided to a respective frequency down-converter
514, the output of which is provided to the GBBF 515, which outputs
signals provided to demodulator and DSP blocks 516.
[0069] Each frequency down-converter 514 receives an RF signal from
an LNA 512 (which RF signal includes data from subscriber terminals
STs, and thus, can be referred to as an RF data signal) and an RF
signal from an LO 452 (which can be referred to as an LO signal),
and uses the LO signal to down-convert the RF data signal to
baseband. The baseband data signal output by each frequency
down-converter 514 is provided to the GBBF 515. The GBBF 515 can be
referred to more specifically as the return link GBBF 515, so as to
distinguish it from the GBBF 230, which can be referred to more
specifically as the forward link GBBF 230. The return link GBBF 515
uses calibration information received from a calibration subsystem,
to produce M baseband spot beams (where, M can equal 1000 beams as
on the forward link, or in some systems, the forward and return
beam counts could be different from one another) Each ofthe M spot
beam signals is provided to a respective demodulator and DSP block
516. Each demodulator and DSP block 516 demodulates the baseband
spot beam signal it receives, and performs digital signal
processing thereon. Such a demodulated data signal can be used to
provide data to, or request data from, a server, client and/or the
like that is coupled to a network (e.g., the network 140 in FIG.
1).
[0070] A gateway (e.g., 105) can have different optics that are
used for transmitting an optical feeder uplink beam (e.g., 102u) to
a space segment (e.g., satellite 100), than the optics that are
used for receiving an optical feeder downlink beam (e.g., 102d)
from a space segment. Alternatively, a gateway can use the same
optics for both transmitting an optical feeder uplink beam (e.g.,
102u) to a space segment and for receiving an optical feeder
downlink beam (e.g., 102d) from a space segment. More specifically,
the RX optics 502 shown in FIG. 5A can be the same as the TX optics
210 shown in FIG. 2A.
[0071] FIG. 5B will now be used to provide details of the return
link GBBF 515 introduced in FIG. 5A, according to certain
embodiments of the present technology. Referring to FIG. 5B, the
GBBF 515 is shown as including a GBBF controller 532 and twenty
five one-to-ten (1 to 10) splitters 534_1 to 534_25. Each
individual splitter 534_1 to 534_25 (which can be referred to
collectively as the splitters 534, or individually as a splitter
534) receives a respective one of the twenty five aggregate signals
(aggregate signal_1, aggregate signal_2 . . . aggregate signal_25)
and outputs ten copies of the aggregate signal received by the
splitter 534. The aggregate signal received by each of the
splitters 524 is an aggregate of ten feed element signals, each of
which corresponds to an output of one of the combiners 420 shown in
and described above with reference to FIG. 4A (which output is
provided to one of the EOMs 434 in FIG. 4B). The ten outputs of
each of the splitters 534 are provided to a different one of ten
frequency down converters (FDCs) 536. Each of the FDCs receives a
different RF signal from a different one of ten local oscillators
(LOs) 516_1 to 516_10 (which can be referred to individually as an
LO 516, or collective as the LOs 516), and thereby frequency shifts
each of the copies of an aggregate signal. This way when the ten
separately frequency shifted copies of the aggregate signal are
passed through a respective one of the filters (FTRs) 538, which
have a common band pass frequency range, the ten feed elements
signals that were included in an aggregate signal are separated
into ten separate feed element signals at the outputs of the FTRs
538. In the embodiment shown in FIG. 5B, there are twenty five
groups of ten FDCs 536, and thus a total of two hundred and fifty
FDCs 536, and there are a total of twenty five groups of ten FTRs
538, and thus a total of two hundred and fifty FTRs 538. In the
manner described above, the outputs of the two hundred and fifty
filters 538 are two hundred and fifty feed element signals that
correspond to the outputs of the FTRs 418 described above with
reference to FIG. 4A. In accordance with certain embodiments, the
functions of the splitters 534, the FDCs 536, the FTRs 538 and the
splitters 540 are performed using a digital signal processor (DSP)
instead of N separate splitters. In other words, a DSP can perform
the signal copying or replication.
[0072] In order to form one thousand spot beams signals from the
two hundred and fifty feed element signals (that are respectively
output from the two hundred and fifty FTRs 538 in FIG. 5B), each of
the feed element signals is provided to a respective one-to-one
thousand (1 to 1000) splitter 540. Each individual splitter 540
receives a respective one of the the two hundred and fifty feed
element signals and outputs one thousand copies of the feed element
signal received by the splitter 540. Each copy of a feed element
signals is provided to a respective phase and amplitude weight
elements 542, which can be implemented in hardware, but are most
likely implemented in software and/or firmware. The GBBF controller
532 uses calibration signals (received from a calibration
subsystem) to derive element specific amplitude and phase
corrections that are provided to the phase and amplitude weight
elements 542, to thereby apply the corrections to the component
element signals provided thereto. An output of each of the phase
and amplitude weight elements 542 is provided to one of one
thousand summers 544_1 to 544_1000 (which can be referred to
individually as a summer 544, or collectively as the summers 544).
The outputs of the summers 544_1 to 544_1000 are the baseband spot
beam signals that are provided to a spot beam to user data
controller 550, which can be considered part of the GBBF 515, or
can be considered external thereto. In the embodiment shown, the
spot beam to user data controller 550 maps the one thousand spot
beam signals output by the summers 544 to ten thousand user data
signals. The user data signals are what can be provided to the
demodulator and DSP blocks 516 shown in FIG. 5A, which was
discussed above.
[0073] The GBBF 515 can be implemented entirely in software.
Alternatively, or additionally, the GBBF 515 can be implemented in
hardware and/or firmware. The outputs of the phase and amplitude
weight elements 542 can be referred to a component element signals.
The outputs of the summers 544, which outputs are referred to as
the baseband spot beam signals above, can also be referred to as
composite signals, since they are a composite of a plurality of
component element signals. The splitters 534 and 540 and the
weighting elements 542 can be collectively referred to as a signal
replication and reverse beamforming weighting unit 533. The same
calibration subsystem that provides calibration signals to the GBBF
controller 232 can provide calibration signals to the GBBF
controller 532.The GBBF controller 532, which receives the
calibration signals, can be the same as the GBBF controller 232, or
distinct therefrom.
[0074] As noted above, a DSP can perform the signal copying or
replication performed by the splitters 534, the FDCs 536, the FTRs
538 and the splitters 540. More generally, all of the functions of
the elements described within the block labeled GBBF 515 can be
implemented by a DSP. In other words, the GBBF 515 can be entirely
or substantially entirely implemented using a DSP. Nevertheless, it
is useful to shown and describe the elements shown in FIG. 5B in
order to understand the operation of such a DSP. The spot beam to
user data controller 550 can also be implemented by the DSP.
[0075] Embodiments of the present technology described herein
enable analog over free space optics (AoFSO) technology to be used
on gateway to/from satellite links, replacing the normal Ku or Ka
or V band spectrum. As described above, analog modulation of a
number of wavelengths of light that are Wavelength Division
Multiplexed (WDM) into a single laser beam from earth to space, and
detected by photodetectors on the satellite. By modulating these
optical wavelengths at the desired RF frequencies, it is possible
to use GBBF, even at high frequencies like Ka band, and with large
numbers of feed elements, due to the high RF bandwidth available at
optical frequencies.
[0076] Currently envisioned free space optical spacecraft
architectures use demodulation of the optical signal, followed by
routing to user link pathways and remodulation of the signal on
user link RF frequencies. Using embodiments of the present
technology described herein it is also possible for ground based
beamforming to be used within a gateway where a channelizer and/or
router onboard a satellite may or may not be present, but the input
segments from the feederlink on the forward link (or to the
feederlink on the return link) are routed to (onboard) feed
elements meant to form user beams (also referred to as spot beams).
In embodiments of the present technology that use ground based
beamforming, the ground system creates and uses the proper
amplitude and phase coefficients to form the desired user beams
(also referred to as spot beams). on a dynamic basis. By contrast,
in an onboard beamforming (OBBF) system, the phase and amplitude
coefficients are typically created onboard a satellite using analog
or digital hardware. In any case, there is a one-to-one
correspondence between the number of feed elements onboard and the
number of feederlink band segments, also referred to as feed
element signals, carrying signals for that feed. With a large
number of feed elements and a high bandwidth per beam, it becomes
impossible to find the feederlink spectrum needed at RF
frequencies, but is not a problem at optical frequencies.
[0077] An advantage of the optical approach for HTS broadcast and
other satellite applications is that it allows for flexible antenna
beam forming with GBBF for large signal bandwidth without the
limitation associated with the available gateway uplink and
downlink spectrum at RF frequencies. This approach allows for the
flexible generation of multiple beams from an array fed reflector.
In addition, in embodiments where the communication signal is
modulated at the transmit (forward) and receive (return) RF
frequencies when applicable no frequency conversion is required on
the satellite, further simplifying the payload design. However for
increased flexibility, frequency conversion can still be applied on
the satellite if desired.
Methods
[0078] FIG. 6 will now be used to summarize methods for enabling a
ground based subsystem (e.g., the gateway forward link equipment
200 in FIG. 2A) to produce and transmit an optical feeder uplink
beam (e.g., 102u in FIG. 1) to a satellite (e.g., 100 in FIG. 1)
that includes a multiple element antenna feed array and that is
configured to receive the optical feeder uplink beam and in
dependence thereon use the multiple element antenna feed array to
produce and transmit a plurality of RF service downlink beams
(e.g., 106d, 110d, 114d and 118d in FIG. 1) to service terminals
ST. In accordance with certain embodiments, a specified RF
frequency range within which the satellite is configured to produce
and transmit a plurality of RF service downlink beams is a downlink
portion of the Ka band. The downlink portion of the Ka band can be
from 17.7 GHz to 20.2 GHz, and thus, have a bandwidth of 2.5 GHz.
Alternatively, the downlink portion of the Ka band can be from 17.3
GHz to 20.2 GHz, and thus, have a bandwidth of 2.9 GHz. These are
just a few examples, which are not intended to be all
encompassing.
[0079] Referring to FIG. 6, step 602 involves performing ground
based beamforming by receiving a plurality of spot beam signals,
producing or otherwise obtaining phase and amplitude beamforming
coefficients, and producing a plurality of feed element signals in
dependence on the plurality of spot beam signals and the phase and
amplitude beamforming coefficients. Step 602 can be performed,
e.g., by the GBBF 230 described above with reference to FIGS. 2A
and 2B. Prior to step 602, the method can involve receiving a set
of user data signals (e.g., ten thousand user data signals), and
combining subsets of the user data signals into the spot beam
signals (e.g., one thousand spot beam signals) that are used for
the ground based beamforming, which steps can be performed by the
user data to spot beam controller 220 discussed above with
reference to FIG. 2A.
[0080] Still referring to FIG. 6, step 604 involves emitting a
plurality of optical signals each having a different peak
wavelength that is within a specified optical wavelength range.
Step 604 can be performed by the lasers 202 described above with
reference to FIG. 2A. The specified optical wavelength range may be
within the C-band and/or L-band optical wavelengths, as explained
above. Further, as explained above, the specified optical
wavelength range can be a contiguous optical wavelength range
within an IR spectrum, or a non-contiguous optical wavelength range
within the IR spectrum. As noted above, visible and/or other
optical wavelengths may alternatively be used.
[0081] Step 606 involves electro-optically modulating each of the
optical carrier signals with one of the feed element signals
produced by the ground based beamforming to thereby produce a
plurality of optical feed element signals. Step 606 can be
performed by the EOMs 204 described above with reference to FIG.
2A. The feed element signals may be frequency up-converted (e.g.,
by the FUCs 244 in FIG. 2A) and filtered (e.g., by the FTRs 246 in
FIG. 2A) prior to the electro-optically modulating
[0082] Step 608 involves multiplexing the plurality of optical data
signals to thereby produce a wavelength division multiplexed
optical signal that includes data for the plurality of RF service
downlink beams. Step 610 can be performed using the WDM MUX 206
discussed above with reference to FIG. 2A.
[0083] Step 610 involves producing an optical feeder uplink beam,
in dependence on the wavelength division multiplexed optical
signal, and step 612 involves transmitting the optical feeder
uplink beam through free-space to the satellite. Steps 610 and 612
can be performed by the transmitter optics 210 discussed above with
reference to FIG. 2A. The optical amplifier (OA) 208 discussed
above with reference to FIG. 2A can also be used to perform step
610.
[0084] In accordance with certain embodiments, each of the
plurality of optical data signals resulting from the
electro-optically modulating at step 608 has an RF frequency within
the same specified RF frequency range within which the satellite
(e.g., 100) is configured to transmit the plurality of RF service
downlink beams. In such embodiments, beneficially, because RF
frequencies of the optical data signals resulting from the
electro-optically modulating are within the same specified RF
frequency range within which the satellite is configured to
transmit the plurality of RF service downlink beams, there is an
elimination of any need for the satellite to perform any frequency
conversions when producing the plurality of RF service downlink
beams in dependence on the optical feeder uplink beam. In other
words, the space segment forward link equipment 300 in FIG. 3
beneficially does not need any frequency down-converters or any
other type of frequency conversion equipment.
[0085] Additional details of step 602 according to certain
embodiments of the present technology, which can be performed by
the GBBF 230 described above with reference to FIGS. 2A and 2B,
will now be described with reference to FIG. 7. More specifically,
FIG. 7 is used to explain additional details of how the ground
based beamforming can be performed at step 602. Referring to FIG.
7, step 702 involves produces multiple copies of each of the spot
beam signals. Step 702 can be performed by the splitters 234
described above with reference to FIG. 2B.
[0086] Still referring to FIG. 7, step 704 involves using the phase
and amplitude coefficients to weight different copies of the spot
beam signals in different manners. Step 704 can be performed by the
weight elements 236 described above with reference to FIG. 2B.
[0087] Step 706 involves summing subsets of the weighted copies of
the spot beam signals to thereby produced the feed element signals.
Step 706 can be performed by the summers 238 described above with
reference to FIG. 2B. The feed element signals produced at step 706
may be frequency up-converted and filtered prior to the
electro-optically modulating that is performed at step 604.
[0088] More generally, steps 702, 704 and 706 can be performed by
the signal replication and forward beamforming weighting unit 233
described above with reference to FIG. 2B.
[0089] Further details of the methods described with reference to
FIGS. 6 and 7 can be appreciated from the above description of
FIGS. 1-5.
[0090] Certain embodiments of the present technology described
above relate to a ground based subsystem for use in transmitting an
optical feeder uplink beam to a satellite that includes a multiple
element antenna feed array and that is configured to input the
optical feeder uplink beam and in dependence thereon use the
multiple element antenna feed array to produce and transmit a
plurality of RF service downlink beams to service terminals. The
ground based subsystem can include a ground based beamformer
(GBBF), a plurality of lasers, a plurality of electro-optical
modulators (EOMs), a wavelength-division multiplexing (WDM), an
optical amplifier, and transmitter optics. The GBBF can be
configured to accept a plurality of spot beam signals, produce or
otherwise obtain phase and amplitude beamforming coefficients, and
output a plurality of feed element signals in dependence on the
plurality of spot beam signals and the phase and amplitude
beamforming coefficients. Each of the lasers can be operable to
emit an optical signal having a different peak wavelength within a
specified optical wavelength range. Each EOM of the plurality of
EOMs can be configured to accept an optical carrier signal from a
respective one of the plurality of lasers, accept a different one
of the plurality of feed element signals from the GBBF, which may
be frequency up-converted and filtered prior to being accepted by
the EOM, and output a respective optical feed element signal in
dependence on the optical carrier signal and the feed element
signal accepted by the EOM. The WDM multiplexer can be configured
to accept the optical feed element signals output by the plurality
of EOMs, and combine the plurality of optical feed element signals
into a wavelength division multiplexed optical signal. The optical
amplifier can be configured to amplify the wavelength division
multiplexed optical signal to thereby produce an optically
amplified wavelength division multiplexed optical signal. The
transmitter optics can be configured to accept the optically
amplified wavelength division multiplexed optical signal and
transmit an optical feeder uplink beam to the satellite in
dependence thereon. The ground based subsystem can also include a
user data to spot beam controller configured to accept a set of
user data signals and combine subsets of the user data signals into
the spot beam signals that are provided to the GBBF.
[0091] In accordance with certain embodiments, the GBBF is further
configured to produce multiple copies of each of the spot beam
signals accepted by the GBBF, use the phase and amplitude
coefficients to weight different copies of the spot beam signals in
different manners, and sum subsets of the weighted copies of the
spot beam signals to thereby produce the feed element signals,
which may be frequency up-converted and filtered prior to being
accepted by the EOMs.
[0092] The ground based subsystem can also include a plurality of
frequency up-converters each of which is configured to frequency-up
convert one of the feed element signals output by the GBBF before
the feed element signal is provided to one of the EOMs. The
frequency up-converters can more specifically be configured to
cause the the optical feed element signals output by the plurality
of EOMs to each have an RF frequency within a same specified RF
frequency range within which the satellite is configured to
transmit the plurality of RF service downlink beams. Additionally,
the ground based subsystem can include a plurality of filters each
of which is configured to filter one of the feed element signals
after the feed element signal has been frequency up-converted, but
prior to the feed element signal being provided to one of the
EOMs.
[0093] In accordance with certain embodiments, the optical feed
element signals output by the plurality of EOMs each have an RF
frequency within a same specified RF frequency range within which
the satellite is configured to transmit the plurality of RF service
downlink beams. In such embodiments, because RF frequencies of the
optical feed element signals output by the plurality of EOMs are
within the same specified RF frequency range within which the
satellite is configured to transmit the plurality of RF service
downlink beams, there is an elimination of any need for the
satellite to perform any frequency conversions when producing the
plurality of RF service downlink beams in dependence on the optical
feeder uplink beam.
[0094] In accordance with certain embodiments, a specified RF
frequency range within which the satellite is configured to produce
and transmit the plurality of RF service downlink beams comprises a
downlink portion of the Ka band. For example, the downlink portion
of the Ka band can be from 17.7 GHz to 20.2 GHz, and thus, have a
bandwidth of 2.5 GHz. For another example, the downlink portion of
the Ka band can be from 17.3 GHz to 20.2 GHz, and thus, have a
bandwidth of 2.9 GHz.
[0095] In accordance with certain embodiments, an optical
wavelength range of the optical feeder uplink beam is a contiguous
or non-contiguous optical wavelength range within an infrared (IR)
spectrum.
[0096] Certain embodiments of the present technology are related to
a method for enabling a ground based subsystem to produce and
transmit an optical feeder uplink beam to a satellite that includes
a multiple element antenna feed array and that is configured to
accept the optical feeder uplink beam and in dependence thereon use
the multiple element antenna feed array to produce and transmit a
plurality of RF service downlink beams to service terminals. Such a
method can include performing ground based beamforming by accepting
a plurality of spot beam signals, producing or otherwise obtaining
phase and amplitude beamforming coefficients, and producing a
plurality of feed element signals in dependence on the plurality of
spot beam signals and the phase and amplitude beamforming
coefficients. The method can also include emitting a plurality of
optical carrier signals each having a different peak wavelength
that is within a specified optical wavelength range, and
electro-optically modulating each of the optical carrier signals
with one of feed element signals produced by the ground based
beamforming to thereby produce a plurality of optical feed element
signals, wherein the feed element signals may be frequency
up-converted and filtered prior to the electro-optically
modulating. The method can further include multiplexing the
plurality of optical feed element signals to thereby produce a
wavelength division multiplexed optical signal that includes data
for the plurality of RF service downlink beams. The method can also
include producing an optical feeder uplink beam, in dependence on
the wavelength division multiplexed optical signal, and
transmitting the optical feeder uplink beam through free-space to
the satellite. A method according to the embodiments described
herein can also include accepting a set of user data signals, and
combining subsets of the user data signals into the spot beam
signals that are used for the ground based beamforming.
[0097] In accordance with certain embodiments, the ground based
beamforming can further include producing multiple copies of each
of the spot beam signals, using the phase and amplitude
coefficients to weight different copies of the spot beam signals in
different manners, and summing subsets of the weighted copies of
the spot beam signals to thereby produced the feed element signals,
which may be frequency up-converted and filtered prior to the
electro-optically modulating.
[0098] A method can also include frequency-up converting and
filtering the feed element signals produced by the ground based
beamforming prior to the electro-optically modulating. The
frequency up-converting can cause the the optical feed element
signals resulting from the electro-optically modulating to each
have an RF frequency within a same specified RF frequency range
within which the satellite is configured to transmit the plurality
of RF service downlink beams.
[0099] In accordance with certain embodiments, the optical feed
element signals resulting from the electro-optically modulating
each have an RF frequency within a same specified RF frequency
range within which the satellite is configured to transmit the
plurality of RF service downlink beams. In such embodiments,
because RF frequencies of the optical feed element resulting from
the electro-optically modulating are within the same specified RF
frequency range within which the satellite is configured to
transmit the plurality of RF service downlink beams, there is an
elimination of any need for the satellite to perform any frequency
conversions when producing the plurality of RF service downlink
beams in dependence on the optical feeder uplink beam.
[0100] Certain embodiments of the present technology are related to
a ground based subsystem for use in transmitting an optical feeder
uplink beam to a satellite that includes a multiple element antenna
feed array and that is configured to accept the optical feeder
uplink beam and in dependence thereon use the multiple element
antenna feed array to produce and transmit a plurality of RF
service downlink beams to service terminals. The ground based
subsystem can include a ground based beamformer (GBBF) including a
GBBF controller, a signal replication and forward beamforming
weighting unit that is controlled by the GBBF controller, and a
plurality of summers. The GBBF controller can be configured to
produce phase and amplitude beamforming coefficients in dependence
on calibration information accepted from a calibration subsystem.
The signal replication and forward beamforming weighting unit can
be configured to replicate each of a plurality of spot beam
signals, weight each of the replicated spot beam signals in
dependence on phase and amplitude beamforming coefficients produced
by the GBBF controller, and output a set of phase and amplitude
weighted signals. The plurality of summers can be configured to sum
respective subsets of the phase and amplitude weighted signals to
thereby produce a plurality of feed element signals. The ground
based subsystem can also include a plurality of lasers, a plurality
of electro-optical modulators (EOMs), a wavelength-division
multiplexing (WDM) multiplexer, an optical amplifier, and
transmitter optics. Each of the lasers can be operable to emit an
optical signal having a different peak wavelength within a
specified optical wavelength range. Each EOM of the plurality of
EOMs can be configured to accept an optical carrier signal from a
respective one of the plurality of lasers, accept a different one
of the plurality of feed element signals from the GBBF, which may
be frequency up-converted and filtered prior to being accepted by
the EOM, and output a respective optical feed element signal in
dependence on the optical carrier signal and the feed element
signal accepted by the EOM. The WDM multiplexer can be configured
to accept the optical feed element signals output by the plurality
of EOMs, and combine the plurality of optical feed element signals
into a wavelength division multiplexed optical signal. The optical
amplifier can be configured to amplify the wavelength division
multiplexed optical signal to thereby produce an optically
amplified wavelength division multiplexed optical signal. The
transmitter optics can be configured to accept the optically
amplified wavelength division multiplexed optical signal and
transmit an optical feeder uplink beam to the satellite in
dependence thereon.
[0101] The foregoing detailed description has been presented for
purposes of illustration and description. It is not intended to be
exhaustive or to limit the subject matter claimed herein to the
precise form(s) disclosed. Many modifications and variations are
possible in light of the above teachings. The described embodiments
were chosen in order to best explain the principles of the
disclosed technology and its practical application to thereby
enable others skilled in the art to best utilize the technology in
various embodiments and with various modifications as are suited to
the particular use contemplated. It is intended that the scope be
defined by the claims appended hereto.
* * * * *